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高周波ランダム振動環境に対する宇宙機構造の設計条件設定に関する研究
https://jaxa.repo.nii.ac.jp/records/22423
https://jaxa.repo.nii.ac.jp/records/22423cecc2fe9-884e-4e7b-afd0-3ef810db82e0
名前 / ファイル | ライセンス | アクション |
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PA1410059.pdf (619.0 kB)
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Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 高周波ランダム振動環境に対する宇宙機構造の設計条件設定に関する研究 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Design; Sound and Acoustics; Random Vibration; Spacecraft Subsystem; Joint Acceptance; Effective Mass; Diffuse Sound Field; Space Engineering | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||
資源タイプ | journal article | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Determination of Design Specification for Random Vibration Environment of Spacecraft Structures | |||||
著者 |
赤城, 弘樹
× 赤城, 弘樹× 安藤, 成将× 柳瀬, 恵一× 施, 勤忠× Akagi, Hiroki× Ando, Shigemasa× Yanagase, Keiichi× Shi, Qinzhong |
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著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
出版者 | ||||||
出版者 | 日本機械学会 | |||||
書誌情報 |
日本機械学會論文集 C編 巻 79, 号 806, p. 3710-3720, 発行日 2013-10 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Spacecraft subsystems with large surface area are exposed to the severe broadband random vibration during its launch. It has been empirically assumed that the dominant source of this random vibration environment is direct acoustic load inside a launch vehicle fairing rather than structural vibration transmission from attachment of spacecraft system. The design of spacecraft subsystems, therefore, have been normally verified by acoustic test. In recent years, however, as the needs for various space missions arise, the number of structurally-complex spacecrafts, which is hard to promptly find dominant source of random vibration, is on the increase. This provides the motivation for the present work in order to determine the critical random vibration environment for the design specification of spacecraft subsystems. In this paper, a simple calculation method employing joint acceptance and effective mass is proposed. This method is applied to small-sized satellite, and the validity of the method is experimentally shown for both diffuse acoustic and random vibration environments. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0387-5024 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN00187463 | |||||
DOI | ||||||
関連タイプ | isVersionOf | |||||
識別子タイプ | DOI | |||||
関連識別子 | http://dx.doi.org/10.1299/kikaic.79.3710 | |||||
関連名称 | info:doi/10.1299/kikaic.79.3710 | |||||
権利 | ||||||
権利情報 | (C)2013 日本機械学会 | |||||
著者版フラグ | ||||||
出版タイプ | AM | |||||
出版タイプResource | http://purl.org/coar/version/c_ab4af688f83e57aa | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: PA1410059000 |